EP2657128A2 - Extrémité de raidisseur améliorant la résistance au délaminage - Google Patents

Extrémité de raidisseur améliorant la résistance au délaminage Download PDF

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Publication number
EP2657128A2
EP2657128A2 EP13164683.8A EP13164683A EP2657128A2 EP 2657128 A2 EP2657128 A2 EP 2657128A2 EP 13164683 A EP13164683 A EP 13164683A EP 2657128 A2 EP2657128 A2 EP 2657128A2
Authority
EP
European Patent Office
Prior art keywords
web
base flange
termination point
flange
top surface
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13164683.8A
Other languages
German (de)
English (en)
Other versions
EP2657128A3 (fr
EP2657128B1 (fr
Inventor
Lyle Ray Deobald
Kenneth L. Brook
Timothy D. Jackson
Kenneth John Duffié
Gregory B. Doty
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Priority to EP17204591.6A priority Critical patent/EP3330172B1/fr
Publication of EP2657128A2 publication Critical patent/EP2657128A2/fr
Publication of EP2657128A3 publication Critical patent/EP2657128A3/fr
Application granted granted Critical
Publication of EP2657128B1 publication Critical patent/EP2657128B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/263—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer having non-uniform thickness
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
    • B32B3/28—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer comprising a deformed thin sheet, i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/16—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating
    • B32B37/18—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with all layers existing as coherent layers before laminating involving the assembly of discrete sheets or panels only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B38/00—Ancillary operations in connection with laminating processes
    • B32B38/0004—Cutting, tearing or severing, e.g. bursting; Cutter details
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—Stringers, longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/08—Reinforcements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2315/00—Other materials containing non-metallic inorganic compounds not provided for in groups B32B2311/00 - B32B2313/04
    • B32B2315/08—Glass
    • B32B2315/085—Glass fiber cloth or fabric
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2607/00—Walls, panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1062—Prior to assembly
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1062—Prior to assembly
    • Y10T156/1064—Partial cutting [e.g., grooving or incising]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24174—Structurally defined web or sheet [e.g., overall dimension, etc.] including sheet or component perpendicular to plane of web or sheet
    • Y10T428/24182—Inward from edge of web or sheet

Definitions

  • Stringers are structural components that are often used to stiffen panels and other structures. With composite panels, composite stringers may be co-bonded, or secondarily bonded, onto the panel to prevent the panel from buckling or otherwise failing when subjected to compressive loads. The combined panel and stringers may then be secured to a substructure.
  • stiffeners provide adequate reinforcement of the corresponding composite panel with respect to compressive loads
  • stiffener runouts, or areas at which the stringers terminate may experience disbonding between the stringers and the panel under certain conditions.
  • the sudden discontinuity of the load path combined with a low composite interlaminar toughness, may result in a structural component that may delaminate or disbond at operational loads.
  • the disbond potential that exists at the stiffener runout locations of a composite structure has been accommodated via various techniques, For example, the architecture of a composite panel may be designed to move the stiffener terminations to an edge of the panel. However, doing so may negatively affect the cost and weight of the corresponding panel. According to an alternative traditional solution, the disbond may be allowed to occur at operational loads and fasteners used to arrest the disbond. With this solution, extensive certification testing is required and any amount of disbond, even though non-critical, may be disconcerting to a customer.
  • Another conventional method for controlling disbond at stiffener runout locations includes the use of flat metallic radius fillers secured to the stiffeners at the termination ends.
  • these conventional radius fillers are not efficient at arresting the disbond under the flange, and provide no arrest capabilities under a web of a stringer.
  • Relatively large mechanically attached metallic fittings may also be used to transfer loads from stringers into the attached composite structure.
  • a disadvantage of these types of fittings is that the fittings increase the weight of the corresponding structure and may be expensive to install, while not completely suppressing the disbond at operational loads.
  • a stiffener runout may include a web and a base flange.
  • the web may be configured in a vertical orientation having a front surface, a rear surface, a bottom edge, and web termination point that is positioned at an outermost location of the web.
  • the base flange may include two flanges extending horizontally from the front and rear surfaces of the web, respectively.
  • the base flange may include a flange termination point that is positioned at an outermost location of the base flange, which is forward of the web termination point.
  • a method of controlling bondline separation between a composite stiffener and a composite structure may be provided.
  • the method may include providing a composite stiffener having a web and a base flange.
  • the web may terminate at a web termination point, while the base flange terminates at a flange termination point that is forward of the web termination point.
  • the base flange may include rounded corners.
  • the web may be trimmed from a full height prior to the web termination point to a reduced height at the web termination point.
  • a recessed notch may be provided within the base flange at the flange termination point, with the web termination point being positioned at the center of the recessed notch.
  • the base flange may be bonded to the composite structure.
  • a stiffener runout assembly may include a stiffener runout, a composite structure bonded to the stiffener runout, a pair of perimeter clamp radius fillers, and a number of fasteners.
  • the stiffener runout may include a web trimmed from a full height to a reduced height at the web termination point at an outermost location of the web.
  • the stiffener runout may also include the base flange that extends horizontally in opposite directions from the web and includes a flange termination point at an outermost location of the base flange. The flange termination point may be positioned forward of the web termination point, with the web termination point positioned within a recessed notch of the base flange.
  • the composite structure may be bonded to the base flange of the stiffener runout at a scarf joint.
  • the pair of perimeter clamp radius fillers may be positioned on a top surface of the base flange on opposing sides of tha web.
  • Each perimeter clamp radius filler may include a bottom surface that is configured to contact the top surface of the base flange around the perimeter of the top surface to create a contact area between the perimeter clamp radius filler and the perimeter of the top surface.
  • the contact area may define a relief cavity between the perimeter clamp radius filler and the top surface of the base flange.
  • the fasteners may secure the perimeter clamp radius fillers to the top surface of the base flange, extending through a top surface of the perimeter clamp radius fillers, through the relief cavities, through the base flange, and through the composite structure.
  • stringer runouts may incorporate various stringer runout aspects, alone or in combination, to prevent disbonding between composite stringers and co-bonded composite structures while minimizing weight and manufacturing complexity and cost.
  • the various embodiments described below will be described within the context of a composite aircraft stringer co-bonded with composite aircraft skin. It should be appreciated that the various embodiments are not limited to these specific components, or to used within aircraft. Rather, the concepts described below may equally apply to any implementation in which a stringer or similar stiffening component is bonded to a composite structure.
  • FIGURE 1 shows a front view of a stiffener runout assembly 100.
  • the stiffener runout assembly 100 includes a stiffener runout 102 co-bonded onto a composite structure 104.
  • the composite structure 104 may be any composite panel, sheet, or other component for which stiffening would be desirable, such as an aircraft skin.
  • the stiffener runout 102 includes a web 106, a base flange 108 that includes a first flange portion 108A and a second flange portion 108B, and a cap 110.
  • a noodle 114 is bonded within the region created between the web 106 and the first and second flange portions 108A and 108B.
  • the web may extend vertically in relation to the composite structure 104.
  • the base flange 108 may be positioned at a bottom edge of the web 106, with the first flange portion 108A extending substantially horizontally from a front surface 120 of the web 106 and the second flange portion 108B extending substantially horizontally from a rear surface 122 of the web 106.
  • the base flange 108 is bonded to the composite structure 104.
  • the stiffener runout assembly 100 may include perimeter clamp radius fillers 112 positioned on the first flange portions 108A and 108B to assist with preventing disbond at the forward edges of the stiffener runout 102.
  • stiffener runout 102 may include additional features and/or varying proportions or configurations as compared to the stiffener runout 102 shown in the figures without departing from the scope of this disclosure.
  • the various figures may not be drawn, to scale and are shown for illustrated purposes only.
  • FIGURES 2 and 3 show top and side views, respectively, of a stiffener runout 102 according to one embodiment.
  • the stiffener runout 102 may include a web 106 and a base flange 108.
  • One such feature includes the rounded corners 202 of the base flange 108.
  • Conventional stiffeners include base flanges that have squared off corners. The square corners are easier to manufacture. Historically, delamination tends to occur at the corners of the base flange first, particularly when a partial shear loading exists. However, by trimming or otherwise creating the rounded corners 202 as shown in FIGURE 2 , the loads through the corners of the base flange 108 are more easily distributed, reducing the potential for delamination at those locations.
  • the base flange 108 terminates at a flange termination point 206.
  • the flange termination point 206 may be the most forward location of the stiffener runout 102.
  • the web 106 terminates at a web termination point 208.
  • Conventional stiffeners include webs and base flanges that terminate at identical locations.
  • the forward edge of a stringer runout is typically stiffer under the web 106 and noodle 114 as compared to the base flange 108. This stiffer central location of the typical stringer forward edge allows for disbonds to occur at this location before occurring at other locations of the base flange 108.
  • the stiffener runout 102 of the various embodiments disclosed herein includes a flange termination point 206 that is forward of the web termination point 208.
  • the web termination point 208 is located within a recessed notch 204, which may be on a semicircular or arcuate edge of the base flange 108 aft of the flange termination point 206. In doing so, any curvature between the termination end of the stiffener runout 102 and the composite structure 104 may be matched, which mitigates the disbonding under the web 106 and noodle 114.
  • the web 106 may be trimmed from a full height 304 to a reduced height 306 at the web termination point 208.
  • the reduced height 306 may be substantially flush with a top surface of the base flanges 108.
  • the loads within the stringer 102 are reduced at the flange termination point 206, which reduces the potential for disbond.
  • reducing the height of the web 106 reduces the stiffness of the stiffener runout 102 along the central axis of the stiffener, which similar to the benefits described above with respect to the recessed notch 204, mitigates the disbonding under the web 106 and noodle 114.
  • the leading edge 302 of the web 106 is tapered according to a curved configuration as shown in FIGURE 3 .
  • An additional feature used to control disbonding includes the use of the perimeter clamp radius fillers 112, as shown in FIGURES 2 and 3 .
  • traditional radius fillers are flat metallic components that may be secured to a base flange in order to provide pressure to the flange and corresponding bond between the flange and the underlying composite structure in an effort to mitigate disbonding.
  • traditional radius fillers do not efficiently handle panel deformation.
  • the traditional radius filler will tend to lift off of the surface, either over the portion of the panel that is deflecting downward, or as that portion of the radius filler deflects downward with the panel, an opposing edge of the traditional radius filler may lift off of the surface.
  • the perimeter clamp radius fillers 112 described herein alleviate these deficiencies of traditional radius fillers by concentrating the clamping force around the perimeter of the base flange 108 where the disbonding is most likely to occur. Moreover, a relief cavity 212 within a central portion of the perimeter clamp radius filler 112 accommodates any deformation of the composite structure 104 and the corresponding base flange 108.
  • the perimeter clamp radius fillers 112 may be metallic, or any other suitable material.
  • each perimeter clamp radius filler 112 includes a bottom surface that projects downward from a portion of the perimeter of the radius filler to create a contact area 210 between the perimeter clamp radius filler 112 and a corresponding portion of the top surface around a perimeter of the base flange 108.
  • the contact area 210 defines the boundaries of the relief cavity 212.
  • Pressure is applied to the base flange 108 by the perimeter clamp radius filler 112 within the contact area 210 to prevent disbonding at the edges of the stiffener runout 102. Because pressure applied to the perimeter clamp radius filler 112 is distributed and concentrated around the perimeter of the base flange 108 while allowing for deformation within the relief cavity 212, the perimeter clamp radius fillers 112 provide a significant advantage over the less effective conventional radius fillers.
  • the contact area 210 may be substantially C-shaped with an opening 216 that provides access to the relief cavity 212 from one edge of the base flange 108.
  • the opening 216 may be positioned along the edge of the base flange 108 opposite the web 106 as shown in FIGURES 2 and 3 since that portion of the edge opposite the web 106 is not highly susceptible to disbonding.
  • the opening 216 may alternatively be positioned at the most rearward edge or any other edge of the base flange 108, and may be configured according to any size and shape.
  • the relief cavity 212 may be filled with a compliant filler, such as a sealant or other material appropriate to the particular application, that allows for deformation without applying pressure to the base flange 108.
  • the opening 216 may provide a passage for excess compliant filler to escape from the relief cavity 212 during installation.
  • Fasteners 214 may be threaded or otherwise placed through corresponding apertures in the perimeter clamp radius filler 112, base flange 108, and composite structure 104. Torque applied to the fasteners 214 transfers force from the perimeter clamp radius filler 112 to the perimeter of the base flange 108 via the contact area 210 to prevent disbonding. Although two fasteners 214 are shown for each perimeter clamp radius filler 112, any number of fasteners 214 may be used without departing from the scope of this disclosure.
  • FIGURES 4 and 5 illustrate two alternative embodiments in which a type of scarf joint 402 is created between the stiffener runout 102 and the composite structure 104.
  • the term "scarf joint" will, be used to refer to a coupling between two or more components in which two of the components are manufactured, or modified to have an angled surface that is engaged with a complementary angled surface of the other component.
  • FIGURE 4 shows a first embodiment in which the composite structure 104 has a uniform thickness, but is bonded to a fiberglass wedge 404. The fiberglass wedge 404 is hatched in the FIGURE 4 to highlight the wedge for clarity purposes only.
  • the fiberglass wedge 404 provides an angled wedge surface 406 that is co-cured into an angled flange surface 408 of the base flange 108.
  • the angled flange surface 408 may be created by reducing the plies of the composite material according to the desired angle and joint length.
  • the fiberglass wedge 404 is highly compliant and is configured to shear load into the composite structure 104 over a longer length, thereby reducing the local moments that may cause disbonding.
  • the fiberglass wedge 404 is described herein as being fiberglass, it should be appreciated that any suitable material that is more compliant (having less stiffness) than the material of the stiffener runout 102 and composite structure 104 may be used to create the wedge.
  • FIGURE 5 shows the second embodiment in which the scarf joint 402 is created by reducing the plies of the composite material according to the desired angle of the angled flange surface 408 and length of the scarf joint 402.
  • the corresponding angled structure surface 502 may be created by increasing plies of the composite material according to the desired angle of the angled structure surface 502 and length of the scarf joint 402.
  • the result is a non-uniform thickness of the base flange 108 that complements a non-uniform thickness of the composite structure 104 within the scarf joint 402.
  • the run to rise ratio associated with the angled structure surface 502 and angled flange surface 408 of the scarf joint 402 is approximately 20:1. According to various embodiments, the ratio may be between 20:1-30:1.
  • the effect of the scarf joint 402 created by altering the plies of the base flange 108 and composite structure 104 as shown in FIGURE 5 is to shear the loads from the stiffener into the composite structure 104 over a relatively long distance. Doing so minimizes the detrimental local moments by reducing the offset in the load line that may initiate disbonding.
  • routine 600 for controlling bondline separation between a stiffener runout 102 and a composite structure 104 will now be described in detail. It should be appreciated that more or fewer operations may be performed than shown in the FIGURE 6 and described herein. Moreover, these operations may also be performed in a different order than those described herein.
  • the routine 600 begins at operation 602, where the stiffener runout 102 having a web 106 and a base flange 108 of composite materials is created. It should be appreciated that other features of a stiffener that are not germans to this disclosure may additionally be created during this or any other operation of the routine 600.
  • creation of the stiffener may commonly include bonding the cap 110 to the top edge of tho web 106, as well as bonding the noodle 114 in the appropriate position between the bottom edge of the web 106 and the first and second flange portions 108A and 108B.
  • the routine 600 continues to operation 604, where the rounded corners 202 of the base flange 108 are created. This operation may be performed by trimming conventional square corners after curing of the base flange 108, or may be a part of the composite molding process.
  • the recessed notch 204 is created in the base flange 108.
  • the recessed notch 204 may be created via trimming material from the base flange 108 or may be created during the material composite molding process.
  • the size and depth of the recessed notch 204 may depend on the particular implementation and the desired distance between the flange termination point 206 and the web termination point 208.
  • the routine 600 continues from operation 606 to operation 608, where the height of the web 106 is trimmed from the full height 304 to the reduced height 306 at the web termination point 208.
  • the leading edge 302 of the web 106 may be trimmed according to a curved configuration or linearly tapered to the reduced height 306.
  • a first method for creating the scarf joint 402 involves utilizing a fiberglass wedge 404 bonded to a top surface of the composite structure 104, providing an angled wedge surface 406 that is co-cured into an angled flange surface 408 of the base flange 108.
  • the angled flange surface 408 of the base flange 108 may be created by dropping plies to create the desired 20:1-30:1 or other ratio at the scarf joint 402.
  • a second method for creating the scarf joint 402 includes dropping plies in the base flange 108 to create the angled flange surface 408 and increasing plies in the composite structure 104 to create the angled structure surface 502. The angled flange surface 408 and the angled structure surface 502 are then co-cured to create the scarf joint 402.
  • the routine 600 continues from operation 610 to operation 612, where the perimeter clamp radius fillers 112 are secured to the base flange 108 with fasteners 214. Torque is applied to the fasteners 214 to concentrate a clamping force within the contact area 210 against the perimeter of the base flange 108 to mitigate disbonding in these areas.
  • the relief cavity 212 is filled with a compliant sealant or other material and the routine 600 ends.
  • loads from the stiffener runout 102 may be sheared into the composite structure 104 at the scarf joint 402 over a relatively long distance to reduce the offset in the load line that could initiate a disbond between the stiffener runout 102 and the composite structure 104.
  • loads may include a first loading condition in which static loads are experienced, such as during a steady straight and level aircraft flight operation.
  • the loads may shift to a second loading condition in which dynamic loads are experienced, such as during a climb, turn, or velocity change.
  • the scarf joint 402 and other features of the stiffener runout 102 described above serve to distribute the loads to the composite structure 104 in a manner that prevents or delays the disbonding that may be present with conventional stringer runouts.
  • a stiffener runout assembly comprising a stiffener runout, comprising a web trimmed from a full height at a location prior to a web termination point to a reduced height at the web termination point at an outermost location of the web, a base flange extending horizontally in opposite directions from the web and including a flange termination point positioned at an outermost location of the base flange, wherein the flange termination point is positioned forward of the web termination point, and wherein the web termination point is positioned within a recessed notch of the base flange; a composite structure bonded to the base flange of the stiffener runout at a scarf joint; a pair of perimeter clamp radius fillers positioned on a top surface of the base flange on opposing sides of the web, each perimeter clamp radius filler comprising a bottom surface configured to contact the top surface of the base flange around a portion of a perimeter of the top surface to create a contact area between the perimeter clamp radius
  • a stiffener runout assembly further comprising a fiberglass wedge positioned between the base flange and the composite structure, wherein the base flange comprises a non-uniform thickness corresponding to a configuration of the fiberglass wedge to create the scarf joint
  • a stiffener runout comprising a web configured in a substantially vertical orientation and including a front surface, a rear surface, a bottom edge, and a web termination point positioned at an outermost location of the web; and a base flange, comprising a first flange portion adjacent to the bottom edge of the web and extending substantially horizontally from the front surface of the web, and a second flange portion adjacent to the bottom edge of the web and extending substantially horizontally from the rear surface of the web, wherein the base flange includes a flange termination point positioned at an outermost location of the base flange, wherein the flange termination point is positioned forward of the web termination point.
  • a stiffener runout further comprising a structure bonded to a bottom surface of the base flange according to a scarf joint.
  • a scarf joint comprising a fiberglass wedge bonded to a top surface of the structure, wherein the structure comprises a substantially uniform thickness, and wherein the base flange comprises a non-uniform thickness corresponding to a configuration of the fiberglass wedge.
  • a stiffener runout wherein the structure comprises a non-uniform thickness, and wherein the base flange comprises a non-uniform thickness corresponding to the non-uniform thickness of the structure.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Connection Of Plates (AREA)
  • Moulding By Coating Moulds (AREA)
  • Body Structure For Vehicles (AREA)
  • Rod-Shaped Construction Members (AREA)
EP13164683.8A 2012-04-25 2013-04-22 Extrémité de raidisseur améliorant la résistance au délaminage Active EP2657128B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP17204591.6A EP3330172B1 (fr) 2012-04-25 2013-04-22 Extrémité de raidisseur améliorant la résistance au délaminage

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/455,217 US8974886B2 (en) 2012-04-25 2012-04-25 Disbond resistant composite stiffener runout

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP17204591.6A Division EP3330172B1 (fr) 2012-04-25 2013-04-22 Extrémité de raidisseur améliorant la résistance au délaminage

Publications (3)

Publication Number Publication Date
EP2657128A2 true EP2657128A2 (fr) 2013-10-30
EP2657128A3 EP2657128A3 (fr) 2015-08-05
EP2657128B1 EP2657128B1 (fr) 2017-12-13

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EP17204591.6A Active EP3330172B1 (fr) 2012-04-25 2013-04-22 Extrémité de raidisseur améliorant la résistance au délaminage
EP13164683.8A Active EP2657128B1 (fr) 2012-04-25 2013-04-22 Extrémité de raidisseur améliorant la résistance au délaminage

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US (3) US8974886B2 (fr)
EP (2) EP3330172B1 (fr)
JP (1) JP6126895B2 (fr)
CN (1) CN103373462B (fr)
CA (1) CA2804837C (fr)
ES (1) ES2661866T3 (fr)

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Also Published As

Publication number Publication date
US10308344B2 (en) 2019-06-04
EP3330172B1 (fr) 2020-11-25
CA2804837A1 (fr) 2013-10-25
US8974886B2 (en) 2015-03-10
EP2657128A3 (fr) 2015-08-05
EP3330172A1 (fr) 2018-06-06
CN103373462A (zh) 2013-10-30
EP2657128B1 (fr) 2017-12-13
US20130287995A1 (en) 2013-10-31
US9676470B2 (en) 2017-06-13
US20150175250A1 (en) 2015-06-25
JP6126895B2 (ja) 2017-05-10
CA2804837C (fr) 2019-12-03
CN103373462B (zh) 2016-08-10
JP2013227014A (ja) 2013-11-07
ES2661866T3 (es) 2018-04-04
US20170246830A1 (en) 2017-08-31

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